EP2942273B1 - Ensemble d'anneau de conjugaison - Google Patents

Ensemble d'anneau de conjugaison Download PDF

Info

Publication number
EP2942273B1
EP2942273B1 EP15164452.3A EP15164452A EP2942273B1 EP 2942273 B1 EP2942273 B1 EP 2942273B1 EP 15164452 A EP15164452 A EP 15164452A EP 2942273 B1 EP2942273 B1 EP 2942273B1
Authority
EP
European Patent Office
Prior art keywords
unison ring
bearing
bearing location
location portion
ring portion
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP15164452.3A
Other languages
German (de)
English (en)
Other versions
EP2942273A2 (fr
EP2942273A3 (fr
Inventor
Christopher Grice
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=51032399&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP2942273(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP2942273A2 publication Critical patent/EP2942273A2/fr
Publication of EP2942273A3 publication Critical patent/EP2942273A3/fr
Application granted granted Critical
Publication of EP2942273B1 publication Critical patent/EP2942273B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/02—Hub construction
    • B64C11/04—Blade mountings
    • B64C11/06—Blade mountings for variable-pitch blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/306—Blade pitch-changing mechanisms specially adapted for contrarotating propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
    • B64C11/48—Units of two or more coaxial propellers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/22—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings
    • F16C19/24—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for radial load mainly

Definitions

  • the present invention relates to a propeller pitch adjusting mechanism and particularly, but not exclusively, to a propeller pitch adjusting mechanism for an aircraft having contra-rotating propellers.
  • US2486016 discloses the preamble of claim 1. It is well known to vary the pitch of the blades on an aircraft propeller, for example in order to maintain the rotational speed of the propeller within close limits. This in turn provides improved performance over a wide range of flight conditions, and enables thrust reversal during landing and ground manoeuvring of the aircraft. It also importantly allows for the feathering of the propeller in the event of an engine shutdown in flight.
  • an unfeathered propeller When an engine is shutdown in flight, an unfeathered propeller can present a large and flat surface to the oncoming airflow if the propellers have a hydraulic failure and do not have a pitch lock mechanism. This will cause a large drag force on the aircraft which can result in a loss of control of the aircraft.
  • a unison ring system comprising:
  • the first unison ring portion controls the pitch of the propeller blades on a first propeller assembly and the second unison ring portion controls the pitch of the propeller blades on a second propeller assembly.
  • the first unison ring portion and the second unison ring portion are separately controllable in order to maintain each of the corresponding first and second propeller assemblies at substantially constant rotational speeds. Movement of the first unison ring portion will closely correspond to movement of the second unison ring portion, although there will be slight variations therebetween.
  • the first unison ring portion and the second unison ring portion are mechanically linked to one another by the bearing, which is housed within the co-operating first and second bearing location portions.
  • the difference in axial length between the bearing and the annular cavity accommodates the slight variation between the independent movement of each of the first unison ring portion and the second unison ring portion during normal control of the respective first and second propeller assemblies.
  • the actuating system of one of the first unison ring portion and the second unison ring portion will drive the failed unison ring portion via the co-operating first and second bearing location portions and bearing.
  • the control of the failed unison ring portion will not be optimal due to the offset resulting from the difference in axial length between the bearing and the annular cavity. However the system will maintain control of the failed unison ring portion which will enable the aircraft to complete its mission albeit at reduced efficiency.
  • the system of the invention will also prevent a propeller overspeed event, which as described above is likely to result in loss of control of the aircraft. This makes the system of the invention convenient and economical for a user.
  • first and second bearing location portions as inner and outer bearing races respectively the system of the invention may be made lighter than an arrangement employing a separate rolling element bearing assembly.
  • the first bearing location portion is integrally formed with the first unison ring.
  • the first bearing location portion is formed as an extension of the first unison ring. This makes the first bearing location portion lighter and stronger and advantageous in weight critical applications.
  • the first bearing location portion is formed as a separate component from the first unison ring and is mechanically attached thereto by, for example, threaded fasteners. This arrangement enables the system of the invention to be retro-fitted to an engine not having such a system.
  • the second bearing location portion is integrally formed with the second unison ring.
  • the second bearing location portion is formed as an extension of the second unison ring. This makes the second bearing location portion lighter and stronger and advantageous in weight critical applications.
  • the second bearing location portion is formed as a separate component from the second unison ring and is mechanically attached thereto by, for example, threaded fasteners.
  • the bearing is a rolling element bearing having an outer race, an inner race, and a plurality of rolling elements accommodated therebetween, the inner race abutting against and axially slidable over the first bearing location portion, and the outer race abutting against and axially slidable over the second bearing location portion.
  • an aircraft powerplant comprising at least one engine, a first propeller assembly, a second propeller assembly and a unison ring system according to the first aspect of the invention, each of the first and second propeller assemblies comprising a plurality of propeller blades, wherein a pitch of the blades of the first propeller assembly is altered by the first unison ring portion and a pitch of the blades of the second propeller assembly is altered by the second unison ring portion.
  • the first propeller assembly rotates in an opposite direction to the second propeller assembly.
  • aspects of the invention provide devices, methods and systems which include and/or implement some or all of the actions described herein.
  • the illustrative aspects of the invention are designed to solve one or more of the problems herein described and/or one or more other problems not discussed.
  • a unison ring system is designated generally by the reference numeral 100.
  • the unison ring system 100 is intended for use in an aircraft powerplant 300 having first and second contra-rotating propellers 320:330, each of the propellers 320:330 being driven by at least one engine 310 (see Figure 4 ).
  • the unison ring system 100 comprises a first unison ring portion 110, a second unison ring portion 140 and a bearing 170.
  • the first unison ring portion 110 is co-axial with the second unison ring portion 140.
  • the first unison ring portion 110 controls the pitch of the blades 340 of the first propeller 320, while the second unison ring portion 140 controls the pitch of the blades 340 of the second propeller 330.
  • the first unison ring portion 110 comprises a first unison ring 120 and a first bearing location portion 130.
  • the second unison ring portion 140 comprises a second unison ring 150 and a second bearing location portion 160.
  • the first bearing location portion 130 is co-axial with the first unison ring 120 and projects axially from the first unison ring 120.
  • the second bearing location portion 160 is co-axial with the second unison ring 150 and projects axially from the second unison ring 150.
  • Each of the first unison ring 120 and the second unison ring 150 have the same geometric form as conventional unison ring components. In other words they have a 'U'-shaped axial cross-section. In use, this 'U'-shaped radial cross section accommodates the lever arms (not shown) that operate to rotate the pitch change spindles (not shown) of the propeller blades (340).
  • the first bearing location portion 130 comprises a radially outwardly opening groove 132.
  • the second bearing location portion 160 comprises a radially inwardly opening groove 162.
  • first unison ring portion 110 and the second unison ring portion 140 are formed from, for example, a titanium alloy material. In other arrangements, the first unison ring portion 110 and the second unison ring portion 140 may be formed from another metal or metal alloy, or from a fibre reinforced composite material.
  • the first unison ring portion 110 and the second unison ring portion 140 are axially positioned along the axis of the propellers 320:330. As outlined above the first unison ring portion 110 and the second unison ring portion 140 are positioned with the first bearing location portion 130 being accommodated concentrically within the second bearing location portion 160.
  • the annular cavity 190 has an axial length 192.
  • the term axial length is understood in the present context to refer to a length in a direction along the axis of rotation of the unison ring system 100.
  • the bearing 170 is located within the annular cavity 190.
  • the bearing 190 is a rolling element bearing having an outer race 176, an inner race 178 and a plurality of rolling elements 180 that are contained between the outer race 176 and the inner race 178.
  • the bearing 170 has an axial length 172,
  • the outer race 176 is in intimate contact with and slidable over the radially inwardly facing surface 164 of the second bearing location portion 160.
  • the inner race 178 is in intimate contact with and slidable over the radially outwardly facing surface 134 of the first bearing location portion 130.
  • outer race 176 is attached to the radially inwardly facing surface 164 while the inner race 178 is in intimate contact with and slidable over the radially outwardly facing surface 134.
  • the inner race 178 is attached to the radially outwardly facing surface 134 while the outer race 176 is in intimate contact with and slidable over the radially inwardly facing surface 164.
  • the axial length 172 of the bearing 170 is less than the axial length 192 of the annular cavity 190.
  • the first unison ring portion 110 is able to move axially relative to the second unison ring portion 140 by a distance equal to the difference between the axial length 192 of the annular cavity 190 and the axial length 172 of the bearing 170.
  • the outer race 176 of the bearing 170 abuts against an axially distal side 166 of the radially inwardly opening groove 162 on the second bearing location portion 160, and the inner race 178 of the bearing 170 abuts against an axially distal side 136 of the radially outwardly opening groove 132 of the first bearing location portion 130.
  • the outer race 176 of the bearing 170 abuts against an axially proximal side 168 of the radially inwardly opening groove 162 on the second bearing location portion 160, and the inner race 178 of the bearing 170 abuts against an axially proximal side 138 of the radially outwardly opening groove 132 of the first bearing location portion 130.
  • the distance being the difference between the axial length 192 of the annular cavity and the axial length 172 of the bearing 170 is predetermined to be greater than the difference between the positions of the first unison ring portion 110 and the second unison ring portion 140 during their normal controlled operation.
  • the remaining operationally controlled unison ring portion can effect control of the failed unison ring portion.
  • both the actuation system for each of the first unison ring portion 110 and the actuation system for the second unison ring portion 140 must be capable of driving both first and second unison ring portions 110,140 in event of the failure of either one of the individual actuation systems.
  • the difference between the axial length 192 of the annular cavity and the axial length 172 of the bearing 170 will mean that in the event of one of the unison ring portions being controlled by the other one of the unison ring portions, there will be a degree of suboptimal operation of the propeller that was controlled by the failed unison ring portion.
  • this sub-optimal control will allow operation of the engine and importantly will allow an operator to safely feather a propeller whose unison ring portion control has failed. As outlined above, this can provide considerable safety benefits to a pilot.
  • a unison ring system according to the embodiment of the invention is designated generally by the reference numeral 200.
  • Features of the unison ring system 200 which correspond to those of the unison ring system 100 have been given corresponding reference numerals for ease of reference.
  • the unison ring system 200 has a first unison ring portion 210, a second unison ring portion 240 and a bearing 270.
  • the first unison ring portion 210 comprises a first unison ring 120 and a first bearing location portion 230.
  • the second unison ring portion 240 comprises a second unison ring 150 and a second bearing location portion 260.
  • first and second unison ring portions 210,240 are identical to the corresponding components of the first embodiment described above with the exception of the first and second bearing location portions 230,260.
  • the first bearing location portion 230 comprises a radially outwardly opening groove 232.
  • the radially outwardly opening groove 232 comprises a radially outwardly facing surface 234 that is formed as an inner bearing race 234.
  • the second bearing location portion 260 comprises a radially inwardly opening groove 262.
  • the radially inwardly opening groove 262 comprises a radially inwardly facing surface 264 that is formed as an outer bearing race 264.
  • the radially outwardly opening groove 232 is arranged facing the radially inwardly opening groove 262 so as to define an annular cavity 290 therebetween.
  • the annular cavity 290 has an axial length 292.
  • the bearing 270 is located within the annular cavity 290.
  • the bearing 290 comprises a plurality of rolling elements 280 that are contained between the outer race 264 and the inner race 234.
  • the bearing 270 has an axial length 272,
  • the plurality of rolling elements 280 are in intimate contact with and slidable over the radially inwardly facing surface 264 of the second bearing location portion, and the radially outwardly facing surface 234 of the first bearing location portion 230.
  • the unison ring system 200 operates according to the same principles as the unison ring system 100 described previously. However in the unison ring system 200 it is the plurality of rolling elements 280 that provide for the interconnection between the first unison ring portion 210 and the second unison ring portion 240 in the event of the failure of the actuation system of one of the unison ring portions.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Support Of The Bearing (AREA)
  • Control Of Turbines (AREA)

Claims (5)

  1. Système d'anneau de conjugaison (200), comprenant :
    une première partie d'anneau de conjugaison (210),
    une deuxième partie d'anneau de conjugaison (240), la deuxième partie d'anneau de conjugaison (240) étant coaxiale avec la partie d'anneau de conjugaison (210) ; et
    un roulement (270) ;
    la première partie d'anneau de conjugaison (210) comprenant :
    un premier anneau de conjugaison (120) ; et
    une première partie d'emplacement de roulement (230) ;
    la deuxième partie d'anneau de conjugaison (240) comprenant :
    un deuxième anneau de conjugaison (150) ; et
    une deuxième partie d'emplacement de roulement (260) ;
    la première partie d'emplacement de roulement (230) étant coaxiale avec le premier anneau de conjugaison (120) et faisant saillie axialement depuis le premier anneau de conjugaison (120), la deuxième partie d'emplacement de roulement (260) étant coaxiale avec le deuxième anneau de conjugaison (150) et faisant saillie axialement depuis le deuxième anneau de conjugaison (150), la première partie d'emplacement de roulement (230) comprenant une cannelure s'ouvrant radialement vers l'extérieur (232), la deuxième partie d'emplacement de roulement (260) comprenant une cannelure s'ouvrant radialement vers l'intérieur (262), la première partie d'anneau de conjugaison (120) et la deuxième partie d'anneau de conjugaison (240) étant positionnées axialement de sorte que la première partie d'emplacement de roulement (230) soit concentrique avec la deuxième partie d'emplacement de roulement (260), en définissant ainsi une cavité annulaire (290) entre elles ;
    le roulement (270) étant logé dans la cavité annulaire (290), une longueur axiale (292) de la cavité annulaire (290) étant supérieure à une longueur axiale (272) du roulement (270) ;
    caractérisé en ce que le roulement (270) comprend une pluralité d'éléments roulants (280), une surface tournée radialement vers l'extérieur (234) de la première partie d'emplacement de roulement (230) étant formée comme une piste de roulement interne (234), une surface tournée radialement vers l'intérieur (264) de la deuxième partie d'emplacement de roulement (260) étant formée comme une piste de roulement externe (264), et la pluralité d'éléments roulants (280) étant disposée entre la première partie d'emplacement de roulement (230) et la deuxième partie d'emplacement de roulement (260).
  2. Système d'anneau de conjugaison (200) selon la revendication 1, la première partie d'emplacement de roulement (230) étant formée de façon intégrale avec le premier anneau de conjugaison (120).
  3. Système d'anneau de conjugaison (200) selon la revendication 1 ou la revendication 2, la deuxième partie d'emplacement de roulement (260) étant formée de façon intégrale avec le deuxième anneau de conjugaison (150).
  4. Motorisation d'aéronef comprenant au moins un moteur, un premier ensemble d'hélice, un deuxième ensemble d'hélice, et un système d'anneau de conjugaison (200) selon une quelconque des revendications 1 à 3, chacun des premier et deuxième ensembles d'hélice comprenant une pluralité de pales d'hélice, un pas des pales du premier ensemble d'hélice étant modifié par la première partie d'anneau de conjugaison (120), et un pas des pales du deuxième ensemble d'hélice étant modifié par la deuxième partie d'anneau de conjugaison (150).
  5. Motorisation d'aéronef selon la revendication 4, le premier ensemble d'hélice tournant dans un sens opposé au deuxième ensemble d'hélice.
EP15164452.3A 2014-05-08 2015-04-21 Ensemble d'anneau de conjugaison Active EP2942273B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GBGB1408103.8A GB201408103D0 (en) 2014-05-08 2014-05-08 A system

Publications (3)

Publication Number Publication Date
EP2942273A2 EP2942273A2 (fr) 2015-11-11
EP2942273A3 EP2942273A3 (fr) 2015-12-09
EP2942273B1 true EP2942273B1 (fr) 2018-07-04

Family

ID=51032399

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15164452.3A Active EP2942273B1 (fr) 2014-05-08 2015-04-21 Ensemble d'anneau de conjugaison

Country Status (3)

Country Link
US (1) US9963221B2 (fr)
EP (1) EP2942273B1 (fr)
GB (1) GB201408103D0 (fr)

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH233498A (de) 1942-03-13 1944-07-31 Ag Messerschmitt Einrichtung an Flugzeugen zum Verstellen hintereinander angeordneter, gegenläufiger Luftschrauben.
US2486016A (en) 1942-11-13 1949-10-25 Rotol Ltd Screw propeller
US4842484A (en) 1983-08-29 1989-06-27 General Electric Company Blade gearing and pitch changing mechanisms for coaxial counterrotating propellers
US4657484A (en) * 1984-09-04 1987-04-14 General Electric Company Blade pitch varying means
US6666585B1 (en) * 2002-07-19 2003-12-23 The Timken Company Unitized cage for cylindrical roller bearing
FR2928977B1 (fr) * 2008-03-21 2010-04-09 Snecma Systeme d'helices contrarotatives disposant d'un dispositif de mise en drapeau des pales d'helices
FR2957329B1 (fr) 2010-03-15 2012-08-03 Snecma Mecanisme de calage variable de pales pour systeme d'helices contrarotatives et systeme d'helices contrarotatives comportant au moins un tel mecanisme
US8336290B2 (en) 2010-09-30 2012-12-25 General Electric Company Pitch change apparatus for counter-rotating propellers
GB201108367D0 (en) 2011-05-19 2011-06-29 Rolls Royce Plc Propulsion engine
GB201202383D0 (en) 2012-02-13 2012-03-28 Rolls Royce Plc A unison ring gear assembly

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
US9963221B2 (en) 2018-05-08
EP2942273A2 (fr) 2015-11-11
US20150321749A1 (en) 2015-11-12
EP2942273A3 (fr) 2015-12-09
GB201408103D0 (en) 2014-06-25

Similar Documents

Publication Publication Date Title
US9302769B2 (en) Ducted rotor for an aircraft and a rotorcraft
US10933985B2 (en) Rolling gimbal lock systems for rotorcraft
US11577829B2 (en) Anti-torque rotor for a helicopter
US20050079053A1 (en) Cyclic actuation system for a controllable pitch propeller and a method of providing aircraft control therewith
EP3366584B1 (fr) Dispositif de commande de pas pour un fenestron d'un giravion
EP3221215B1 (fr) Plateau oscillant renforcé par un composant composite
EP3753849B1 (fr) Rotor anticouple pour hélicoptère
EP3141476B1 (fr) Mécanisme de changement de pas pour rotor de soufflante
EP2703288B1 (fr) Actionneur électromécanique linéaire pour commande de rotor de pale
EP2942273B1 (fr) Ensemble d'anneau de conjugaison
EP2525046B1 (fr) Moteur de propulsion
EP3181448A1 (fr) Générateurs de tourbillons et procédé de création de remous sur un avion
US20200102072A1 (en) Rotorcraft Masts having a Nonintegral Raceway
EP3599167B1 (fr) Butée annulaire anti-battement dotée d'éléments d'usure amovibles
EP3757003B1 (fr) Rotor anticouple pour hélicoptère
US11433996B2 (en) Lightweight low drag rotor pitch beam
EP3693267B1 (fr) Moyeu à faible frottement de rotor
EP4201810A1 (fr) Commande électromécanique de pas de pale
EP2960151A1 (fr) Ensemble d'anneau de commande
RU176027U1 (ru) Вертолет с соосными несущими винтами

Legal Events

Date Code Title Description
PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIC1 Information provided on ipc code assigned before grant

Ipc: B64C 11/30 20060101ALI20151105BHEP

Ipc: B64C 11/48 20060101AFI20151105BHEP

17P Request for examination filed

Effective date: 20160602

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20180406

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1014203

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180715

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602015012896

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20180704

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1014203

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180704

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181104

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181004

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181005

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181004

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

REG Reference to a national code

Ref country code: DE

Ref legal event code: R026

Ref document number: 602015012896

Country of ref document: DE

PLBI Opposition filed

Free format text: ORIGINAL CODE: 0009260

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

26 Opposition filed

Opponent name: UNITED TECHNOLOGIES CORPORATION

Effective date: 20190208

PLAX Notice of opposition and request to file observation + time limit sent

Free format text: ORIGINAL CODE: EPIDOSNOBS2

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

PLBB Reply of patent proprietor to notice(s) of opposition received

Free format text: ORIGINAL CODE: EPIDOSNOBS3

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20190430

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190421

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190430

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190430

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: ROLLS-ROYCE PLC

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190430

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190421

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181104

PLAB Opposition data, opponent's data or that of the opponent's representative modified

Free format text: ORIGINAL CODE: 0009299OPPO

R26 Opposition filed (corrected)

Opponent name: RAYTHEON TECHNOLOGIES CORPORATION

Effective date: 20200724

APBM Appeal reference recorded

Free format text: ORIGINAL CODE: EPIDOSNREFNO

APBP Date of receipt of notice of appeal recorded

Free format text: ORIGINAL CODE: EPIDOSNNOA2O

APAH Appeal reference modified

Free format text: ORIGINAL CODE: EPIDOSCREFNO

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

APBQ Date of receipt of statement of grounds of appeal recorded

Free format text: ORIGINAL CODE: EPIDOSNNOA3O

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20150421

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

APBU Appeal procedure closed

Free format text: ORIGINAL CODE: EPIDOSNNOA9O

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230528

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230421

Year of fee payment: 9

Ref country code: DE

Payment date: 20230427

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20230418

Year of fee payment: 9

PLAY Examination report in opposition despatched + time limit

Free format text: ORIGINAL CODE: EPIDOSNORE2

PLBC Reply to examination report in opposition received

Free format text: ORIGINAL CODE: EPIDOSNORE3